Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(fx73170a-il) WORTMANN FX 73-170 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-170 A airfoil Max thickness 17.1% at 43.5% chord Max camber 5.6% at 43.5% chord Max Cl/Cd 17.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Max Cl/Cd 17.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n6h15-il) NACA 6-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-15 rotorcraft airfoil Max thickness 15.6% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 17.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(griffith30symsuction-il) Griffith 30% Suction Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Griffith 30% suction airfoil Max thickness 30.6% at 49.3% chord Max camber 0% at 0% chord Max Cl/Cd 17.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Max Cl/Cd 17.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(n5h20-il) NACA 5-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 17 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20402-il) NASA SC(2)-0402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord Max Cl/Cd 16.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fxs02196-il) FX S 02-196 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.7% at 43.5% chord Max Cl/Cd 16.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s818-nr) NREL's S818 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord Max Cl/Cd 16.7 at Re# 100,000 Source NWTC National WInd Technology Center
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord Max Cl/Cd 16.7 at Re# 100,000 Source Generated